Rotating wing for aircraft



SQPfi. 27,, 1949. RENQUX 2,432,936

ROTATING WING FOR AIRCRAFT Filed Feb 7, 19 16 l i l i 2/ 20 1 I I T Fi mvroe ATTORNEW.

Patented Sept. 27 1949 .hpplicati'on ebruary 7, 191%, S erlialNo; 8 563 24 lit-France Feline-W 3, 1942 Y ,Section 1, Public Law 690, August 8, 19 18 Patent expires February 3, 19.62

4'Claim'5. (Cl. it'll-Q159 The invention consists of a new method, in the constructionof the supporting blades for apparatus with revoiv ing wing's.

It is known that. in apparatus of this kind, the blades, owing to their conditions of operation, are generally o fgreat length and small section, also that they are requiredtohave great -strength in order to withstandthe strains "to which they are subjected, strainswhlchare manifold, varying and alternating constantiyjowmg to the rotation. These strains react throughout the blade.

It will at once be realisedthat it is extremely dangerous to Weaken Itheconstructive components of these blades by bolt holes, rivet or pin holes or others, including nicks, ten'ons and weldings.

Now on the one hand in the present processes of construction, bolts,.split pins and other methods of joining up are indispensable, while on the other hand they represent dangers :or breakage which must be avoided.

This therefore constitutes a problem, the practical solution of which seems to be always to design a principal supporting compo'ntan't, such as a main beam, ofgre'at length and small section,

which is able to receive and tohold strongly the 1' constructive components essential :for the production of a blade for rotating wings but containing no weakening agencies either in the form of bolt or pin holes or others'. a

A construction of this kind is provided by the subject of the present invention which consists essentially of a longitudinal "member of special section which permits of applying a process of mounting and fixing in-wliichbolt's, pins, etc. are

excluded. 7 h

Thi'sis the longitudinal member of particular section which characterises the present method of mounting shown on'the -=drawings annexed given by way f explanation and also as an example of construction of one of the forms which the subject of the invention may take.

According to these drawings: v v

Figure 1 is a-plan, with --3eining lines, of the whole of a supporting blade for revolving Wings designed according to the new process; Fig. 2

shows on a larger scale and in cross-section, the process of mounting and fixing the secondary component on the principal component formed by a sectional longitudinal member; Fig. 3 is a perspective View of apart of the mounting and fixing shown on Fig. 1; Figs. 4, 5 and 6 are respectively, again in cross-section, some modifications in the sectional form of the longitudinal members; Fig. 7 shows illustrated under the same conditions as Fig. 2, the use of the longitudinal member according to radiations of form shew-n ohFigs. 4,5 and it. v

'In the exampiessncwn here, which are not restrictedthelongitudinai meinber I forming "the principal components! the blade a section of speciaI form coma g-mci-e favourably Within the prismatic rang-e itlaas tine-orseverai grooves 2, 3 and 4, and 5, longitudinal, preferably covetaiio'r equivaientsnape. "The secondary B are ribs which are more clearly ible'on'Tig-s; 2, '3 "and 7. They carry hooking-on I 'tn'e'prcme of Wh'ichfits exactly and without pinyin the'grccves 2 and 3. however these components 3 are generally which permits them -'easily in the" longitudinal- "members by passing them bb'liquely-betweh the 2 and '3 and then "'trai'g'hteni-ii 'g them cut, perpendicularly to the plane of the biade-,--pi-otisicn is made for lining them with man pistes 8of triangular form, the base of Whili' foi'ii' s, byaeiustment, a male part entering accurately into the profile determined by the grooves 2 and'S, Fig. 2 ora female partcoactingwitn 9 and N, Fig. 17. in'tnis iatter mod-e of fitting; slightly different from that shown on; -his. the'plates l are put at ll, which'gives them ome elasticitywhich will, atthe time when they are fixed on'the component 6, allow them to wen ughtiy and teemse up in the slots 9 and m in theiiireotion er the arrows, being held thereby 'theiriccking points 1P2 ans ii. The distaneeapartoft eseccnaarycem onentsis maintamed by stays ll, Fig. 3 in tum enter the slo't's '2 ands or thee its a ane -m, Fig. '2.

same method crattacnment be util'ised for th'ein'ember 15 which forms the impact edge or the made and 'Wliibh can "if desired, be same asshown lungs-Janene 7 or hollowed out n Fig. '4. Theloek iiigo'f thii'iernbr 15 onto as i thefl' ongitiidiha l ineii bei' 1 by'ineahs or the slots '4 and *5 is again cbtaineu by the use 01' an elasticity' slot "I -6 which snows the expansion or the member 15 as Figs; and 3 o? its contracticjn as in Fig. 7 according to Whether the "bolt I] with a tapered head is placed horizontally or vertically to the slot 16. Alternatively the looking by expansion of the member l5 in the slots 4 and 5 can be effected by the insertion of a bar I8 of suitable cross section to act as a wedge. as shown in Fig. 4.

The longitudinal locking of all the secondary components 6, the stays l4 and the impact edge [5 is ensured by a stop l9, Fig. 1, adjustable and of known operation, supported on the end part 29 assembled to the longitudinal member I in that part where the strains to be borne by the latter are feeble and the usual methods of assemblage no longer present any danger of breakage.

In the example illustrated the longitudinal member I is connected by a suitable mounting 2| to the driving shaft 22.

The use of this process of fitting and assemblage without bolts, pins or other means producing a weakening of the sections is a very considerable advance in the design of a blade for revolving wings, an advance determined by the industrial result obtained, likewise considered as new, which is that of using a longitudinal member the section of which shows no weakening, and which, owing to its special section, allows of receiving and fixing without bolts, pins, weldings or other all the secondary elements needed for the production of a revolving or stationary blade.

It is obvious that according to the size of the blade, the character and mode of attachment of the secondary components, the latter can be fitted to the impact edge or conversely. Inlike manner the dovetail shape of the grooves may vary as likewise the dimensions and the disposition without on that account altering the general conception of the inventionwhich has just been described or its industrial result.

Iclaim:

1. In a rotating wing and blade for aircraft, a central longitudinal spar, upper and lower aerodynamically curved surfaces thereon, longitudinal dovetail grooves at the front and rear of said spar, a forward part for the wing, a longitudinal tenon on said forward part to engage in thegroove at the front of the spar, whereby the forward part may be rigidly attached to said spar, a hollow rear portion for the wing, transverse ribs in the rear portion, tenons carried by said ribs to engage in the groove at the rear of the spar whereby the rear portion may be rigidly attached to the spar, and spacing membersdisposed in the groove at the rear of the spar to abut against the tenons and thereby retain the ribs in parallel position.

2. In a rotating win and blade for aircraft, a central longitudinal spar, upper and lower aerodynamically curved surfaces thereon, longitudinal dovetail grooves at the front and :rear of said spar, a hollow forward part for the wing, a longitudinal tenon on said forward part to engage in the longitudinal groove at the front of the spar and thereby serve to attach the forward part to the spar, a slot in said tenon to impart resiliency thereto, an adjustable wedge in said slot whereby the tenon may be expanded to engage more firmly in the groove at the front of the spar, a hollow rear portion for the wing, fiat transverse ribs in' the rear portion, plates attached at the forward end of each of the ribs, tenons at the forward part of such plates to engage in the groove at the rear of the spar and thereby serve to attach the rear portion to the spar, and resilient spacing members engaged in the groove at the rear of the spar and abutting on the tenons of the plates, thereby serving to retain the ribs in parallel position.

the forward part to impart resiliency to the tenon and permit springing of the tenon into the groove at the front of the spar, a hollow rear portion for the wing, transverse ribs in the rear portion, plates at one end of each such rib, tenons carried by said plates engaged in the groove at the rear of the spar, and spacing members engaged in the groove at the rear of the spar abutting at their ends on the plates, whereby the ribs are retained in parallel position.

, 4. In a rotating wing and blade for aircraft, a central longitudinal spar, upper and lower aerodynamically. curved surfaces thereon, longitudinal dovetail rooves at thefront and rear of said spar, a forward part for the wing, a longitudinal tenon atthe rear of said forward part to engage in the groove at the front of the spar andthereby serve to attach the forwardpart to the spar, a slot in the tenon to impart resiliency thereto, bolts disposed -in the slot, a tapered head on said bolts engaged in the slot whereby when the bolts are tightened the tapered heads thereof move into the slot and cause the tenon to expand and engage more firmly in the groove at the front of the spar, a hollow rear portion for the wing, flat transverse ribs running fore and aft of the rear portion in upright position, substantially triangular plates attached at the forward end .of each said rib, tenons at the front end of such plates to engage in the groove at the rear of the spar and thereby serve to attach the rear portion to the spar, and curved longitudinal resilient spacing plates engaged .at both .their longitudinal edges in the groove at the rear of the spar and abutting at their ends on the plates, whereby the ribs are retained in parallel position.

PIERRE EDOUARD RENOUX.

REFERENCES CITED The following references are of record in the file of this patent:

' UNITED s'rA'rEs ,PATENTS 

